Experimental Investigation Of Base Pressure On Blunt Trailing Edge Wings At Supersonic Velocities
Download Experimental Investigation Of Base Pressure On Blunt Trailing Edge Wings At Supersonic Velocities PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Experimental Investigation Of Base Pressure On Blunt Trailing Edge Wings At Supersonic Velocities book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages.
Experimental Investigation of Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.
Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.